2 A jet aircraft with the mass, wing area and drag polar values given in Q1 has CLmax=1.9 and a thrust-to-weight ratio = 0.2 at ISA sea-level conditions. Assuming flight at full throttle (i.e. maximum thrust) and ISA sea level conditions, calculate: (a) Steady rate of climb and corresponding climb angle at a speed 20% above stall speed; (b) Lift coefficient, turn rate and radius, and true air-speed in a 50 degree correctly banked level turn. [15] [15] [30 marks]